Finite element analysis of composites materials for aerospace applications
Composites materials are intended to be used more extensively as an alternative of aluminum structure in aircraft and aerospace applications. This is due to their attractive properties as high strength-to-weight ratio and stiffness-to-weight ratio. Besides that it clarifies the growing interest for...
| Main Authors: | , , , , |
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| Format: | Article |
| Language: | English English |
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2010
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| Online Access: | http://psasir.upm.edu.my/id/eprint/11950/1/Finite%20element%20analysis%20of%20composites%20materials%20for%20aerospace%20applications.pdf |
| _version_ | 1825944963094937600 |
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| author | Mohamad, Nurhaniza Mohd Atan, Kamel Ariffin Ali, Aidy Mustapha, Faizal Abdul Wahab, Noraini |
| author_facet | Mohamad, Nurhaniza Mohd Atan, Kamel Ariffin Ali, Aidy Mustapha, Faizal Abdul Wahab, Noraini |
| author_sort | Mohamad, Nurhaniza |
| collection | UPM |
| description | Composites materials are intended to be used more extensively as an alternative of aluminum structure in aircraft and aerospace applications. This is due to their attractive properties as high strength-to-weight ratio and stiffness-to-weight ratio. Besides that it clarifies the growing interest for composites materials due to advantages of lightweight, high strength, high stiffness, superior fatigue life, tremendous corrosion resistance and low cost manufacturing. In this study, a finite element analysis (FEA) of fiberglass unidirectional E-type was analyzed in the framework of ABAQUS finite element commercial software. The analysis was done to quantify the mechanical properties and response of unidirectional E-glass in term of tensile, compression and thermal responses. From the analysis, the maximum and minimum values of stress and strain for E-glass 21xK43 Gevetex and Silenka E-glass 1200tex were obtained and stress-strain curve is presented. The ultimate load of failure, elastic behavior, tensile strength and other properties for each laminated plates under tensile and thermal-stress are determined from stress-strain curves. The simulation will run twice for each material where the first simulation based on orientation angles of 45° for ply-1, -45° for ply-2 and 90° for ply-3 while the second simulation, the orientation angles is 0° for all plies. The simulation is successfully conducted and verified by experimental data.
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| first_indexed | 2024-03-06T07:24:07Z |
| format | Article |
| id | upm.eprints-11950 |
| institution | Universiti Putra Malaysia |
| language | English English |
| last_indexed | 2024-03-06T07:24:07Z |
| publishDate | 2010 |
| record_format | dspace |
| spelling | upm.eprints-119502015-10-21T02:55:43Z http://psasir.upm.edu.my/id/eprint/11950/ Finite element analysis of composites materials for aerospace applications Mohamad, Nurhaniza Mohd Atan, Kamel Ariffin Ali, Aidy Mustapha, Faizal Abdul Wahab, Noraini Composites materials are intended to be used more extensively as an alternative of aluminum structure in aircraft and aerospace applications. This is due to their attractive properties as high strength-to-weight ratio and stiffness-to-weight ratio. Besides that it clarifies the growing interest for composites materials due to advantages of lightweight, high strength, high stiffness, superior fatigue life, tremendous corrosion resistance and low cost manufacturing. In this study, a finite element analysis (FEA) of fiberglass unidirectional E-type was analyzed in the framework of ABAQUS finite element commercial software. The analysis was done to quantify the mechanical properties and response of unidirectional E-glass in term of tensile, compression and thermal responses. From the analysis, the maximum and minimum values of stress and strain for E-glass 21xK43 Gevetex and Silenka E-glass 1200tex were obtained and stress-strain curve is presented. The ultimate load of failure, elastic behavior, tensile strength and other properties for each laminated plates under tensile and thermal-stress are determined from stress-strain curves. The simulation will run twice for each material where the first simulation based on orientation angles of 45° for ply-1, -45° for ply-2 and 90° for ply-3 while the second simulation, the orientation angles is 0° for all plies. The simulation is successfully conducted and verified by experimental data. 2010 Article PeerReviewed application/pdf en http://psasir.upm.edu.my/id/eprint/11950/1/Finite%20element%20analysis%20of%20composites%20materials%20for%20aerospace%20applications.pdf Mohamad, Nurhaniza and Mohd Atan, Kamel Ariffin and Ali, Aidy and Mustapha, Faizal and Abdul Wahab, Noraini (2010) Finite element analysis of composites materials for aerospace applications. IOP Conference Series: Materials Science and Engineering, 11 (1). ISSN 1757-899X 10.1088/1757-899X/11/1/012010 English |
| spellingShingle | Mohamad, Nurhaniza Mohd Atan, Kamel Ariffin Ali, Aidy Mustapha, Faizal Abdul Wahab, Noraini Finite element analysis of composites materials for aerospace applications |
| title | Finite element analysis of composites materials for aerospace applications
|
| title_full | Finite element analysis of composites materials for aerospace applications
|
| title_fullStr | Finite element analysis of composites materials for aerospace applications
|
| title_full_unstemmed | Finite element analysis of composites materials for aerospace applications
|
| title_short | Finite element analysis of composites materials for aerospace applications
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| title_sort | finite element analysis of composites materials for aerospace applications |
| url | http://psasir.upm.edu.my/id/eprint/11950/1/Finite%20element%20analysis%20of%20composites%20materials%20for%20aerospace%20applications.pdf |
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